Abstract
Experiments were made to find the drag on the fore portion of a circular cone in a rarefied supersonic flow. Wind-tunnel tests on a cone of 15 deg half angle were conducted over a range of Reynolds number (based on freestream properties and cone slant length) of 70 to 1500 at Mach 2 and 500 to 7000 at Mach 4. The experimental drag curves are in fair agreement wi th available boundary layer predictions if certain induced pressure and tranverse curvature effects are included, a l though some difference in trend of the experimental and theoretical curves is evident.
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